Energy flow

ABSTRACT

An airplane is provided. The airplane includes a compressing device including a turbine and a compressor. The turbine includes first and second inlets and provides energy by expanding one or more mediums. The first inlet is receives a first medium of the one or more mediums. The second inlet receives a second medium of the one or more mediums. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode.

CROSS-REFERENCE TO RELATED APPLICATION

This application claims benefit of priority to U.S. ProvisionalApplication No. 62/341,950 filed May 26, 2016, the disclosure of whichis incorporated herein by reference in its entirety.

BACKGROUND

In general, contemporary air condition systems are supplied a pressureat cruise that is approximately 30 psig to 35 psig. The trend in theaerospace industry today is towards systems with higher efficiency. Oneapproach to improve airplane efficiency is to eliminate the bleed airentirely and use electrical power to compress outside air. A secondapproach is to use lower engine pressure. The third approach is to usethe energy in the bleed air to compress outside air and bring it intothe cabin.

BRIEF DESCRIPTION

According to one or more embodiments, a compressing device is provided.The compressing device comprises a turbine comprising a first inlet anda second inlet and configured to provide energy by expanding one or moremediums. The first inlet is configured to receive a first medium of theone or more mediums. The second inlet is configured to receive a secondmedium of the one or more mediums. The compressing device comprises acompressor configured to receive a first energy derived from the firstand second mediums being expanded across the turbine during a first modeof the compressing device, receive a second energy derived from thefirst medium being expanded across the turbine during a second mode ofthe compressing device, and compress the second medium in accordancewith the first mode or the second mode.

According to one or more embodiments or the above compressing deviceembodiment, the compressing device can comprise a fan configured toreceive the first energy during the first mode and the second energyduring the second mode.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a power turbineconfigured to provide a third energy by expanding a third medium of theone or more mediums, wherein the compressor is configured to receive thethird energy from the third medium expanded across the power turbine.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the turbine and the compressor; and a secondcomponent, which is separate from the first component, comprising a fan,a second turbine, and a shaft.

According to one or more embodiments or any of the above compressingdevice embodiments, the fan can be driven via the shaft by the firstmedium expanding across the second turbine.

According to one or more embodiments or the airplane embodiment above,the compressing device can comprise a first component comprising theturbine and the compressor; and a second component, which is separatefrom the first component, comprising a fan driven by a motor.

According to one or more embodiments or any of the above compressingdevice embodiments, the first medium and the second medium can be mixedat the turbine during the first mode.

According to one or more embodiments or any of the above compressingdevice embodiments, the first medium and the second medium are mixeddownstream of the turbine during the second mode.

According to one or more embodiments or any of the above compressingdevice embodiments, the first medium can be bleed air and the secondmedium can be fresh air.

According to one or more embodiments, an environmental control system ofan aircraft can comprises any of the above compressing deviceembodiments.

According to one or more embodiments, a compressing device is provided.The compressing device comprises a first turbine configured to provide afirst energy by expanding a first medium; a second turbine configured toprovide a second energy by expanding a second medium; and a compressor.The compressor is configured to receive the first energy and the secondenergy during a first mode of the compressing device, receive the firstenergy during a second mode of the compressing device, and compress thesecond medium in accordance with the first mode or the second mode.

According to one or more embodiments or the above compressing deviceembodiment, the compressing device can comprise a fan configured toreceive: the first energy and the second energy during the first mode,and the first energy during the second mode.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the first turbine, the second turbine, and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan, a third turbine, and a shaft.

According to one or more embodiments or any of the above compressingdevice embodiments, the fan can be driven via the shaft by the firstmedium expanding across the second turbine.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the first turbine, the second turbine, and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan driven by a motor.

According to one or more embodiments or any of the above compressingdevice embodiments, the second turbine can comprise a dual entry turbineconfigured to operate as a power turbine during a second mode byexpanding a third medium to provide a third to the compressor.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the first turbine, the second turbine, and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan, a third turbine, and a shaft.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the first turbine, the second turbine, and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan driven by a motor.

According to one or more embodiments, a compressing device is provided.The compressing device comprises a first turbine configured to receiveand expand a first medium; a second turbine configured to receive andexpand a second medium; and a compressor. The compressor is configuredto receive a first energy from the expansion of the first medium by thefirst turbine, and compress the second medium in the first energy; and afan configured to receive a second energy from the expansion of thesecond medium by the second turbine.

According to one or more embodiments or the above compressing deviceembodiment, the compressing device can comprise a power turbineconfigured to provide a third energy by expanding a third medium,wherein the compressor is configured to receive the third energy fromthe third medium expanded across the power turbine.

According to one or more embodiments, a compressing device is provided.The compressing device comprises a turbine comprising a first inletconfigured to receive a mixture of a first medium and a second mediumand a second inlet configured to receive the first medium, wherein theturbine is configured to provide a first energy by expanding the mixtureand to provide a second energy by expanding the first medium. Thecompressing device comprises a compressor configured to receive thefirst energy from the turbine during a first mode of the compressingdevice, receive the second energy from the first medium during a secondmode of the compressing device, and compress the second medium inaccordance with the first mode or the second mode.

According to one or more embodiments or the above compressing deviceembodiment, the compressing device can comprise a fan configured toreceive the first energy during the first mode and the second energyduring the second mode.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a power turbineconfigured to provide a third energy by expanding a third medium,wherein the compressor is configured to receive the third energy fromthe third medium expanded across the power turbine.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the turbine and the compressor; and a secondcomponent, which is separate from the first component, comprising a fan,a second turbine, and a shaft.

According to one or more embodiments or any of the above compressingdevice embodiments, the fan can be driven via the shaft by the firstmedium expanding across the second turbine.

According to one or more embodiments or any of the above compressingdevice embodiments, the compressing device can comprise a firstcomponent comprising the turbine and the compressor; and a secondcomponent, which is separate from the first component, comprising a fandriven by a motor.

Additional features and advantages are realized through the techniquesof the embodiments herein. Other embodiments are described in detailherein and are considered a part of the claims. For a betterunderstanding of the embodiments with the advantages and the features,refer to the description and to the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter is particularly pointed out and distinctly claimed inthe claims at the conclusion of the specification. The forgoing andother features, and advantages thereof are apparent from the followingdetailed description taken in conjunction with the accompanying drawingsin which:

FIG. 1 is a diagram of a schematic of an environmental control systemaccording to an embodiment;

FIG. 2 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 3 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 4 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 5 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 6 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 7 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 8 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 9 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 10 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 11 is a diagram of a schematic of an environmental control systemaccording to another embodiment;

FIG. 12 is a diagram of a schematic of an environmental control systemaccording to another embodiment; and

FIG. 13 is a diagram of a schematic of an environmental control systemaccording to another embodiment.

DETAILED DESCRIPTION

A detailed description of one or more embodiments of the disclosedapparatus and method are presented herein by way of exemplification andnot limitation with reference to the FIGS.

Embodiments herein provide an environmental control system of anaircraft that mixes mediums from different sources and uses thedifferent energy sources to power the environmental control system andto provide cabin pressurization and cooling at high fuel burnefficiency. The medium can generally be air, while other examplesinclude gases, liquids, fluidized solids, or slurries.

Turning to FIG. 1, a schematic of an environmental control system isdepicted according to a non-limiting embodiment (i.e., a system 100), asit could be installed on an aircraft. The aircraft example is notintended to be limiting, as alternative embodiments are contemplated

As shown in FIG. 1, the system 100 can receive a first medium F1 from aninlet 101 and provide a conditioned form of the first medium F1, asindicated by thin-solid-lined arrows, which eventually is a portion of amixed medium (described herein) provided to a volume 102. In view of theabove aircraft embodiment, the first medium F1 can be bleed air, whichis pressurized air supplied to or originating from (being “bled” from)an engine or auxiliary power unit of the aircraft. Note thattemperature, humidity, and pressure of the bleed air can vary widelydepending upon a compressor stage and revolutions per minute of theengine. Generally, the bleed air described herein is high-pressure air.The volume 102 can be pressurized air within an aircraft cabin or acombined flight deck and aircraft cabin. Generally, the pressurized airdescribed herein is at a pressure that creates a safe and comfortableenvironment for humans on the aircraft.

The system 100 can receive a second medium F2 from an inlet 103 andprovide a conditioned form of the second medium F2, as indicated bydotted-lined arrows, which eventually is a portion of the mixed mediumprovided to the volume 102. The second medium F2 can be fresh air, whichcan be outside air destined to enter the volume 102. The outside air canbe procured by one or more scooping mechanisms, such as an impact scoopor a flush scoop. Thus, the inlet 103 can be considered a fresh airinlet or an outside air inlet. Generally, the fresh air described hereinis at an ambient pressure outside of the aircraft with respect toaltitude.

The system 100 can further receive a third medium F3 from the volume102, as indicated by dot-dashed-lined arrows. The third medium F3 can becabin discharge air, which can be air leaving the volume 102 anddumped/discharged overboard. For example, the cabin discharge air can besupplied to a destination, such as an outlet 104. Examples of the outlet104 can include, but are not limited to, a ram circuit (which exhaustsoverboard) and/or an outflow valve (which exhausts overboard).

In accordance with non-limiting embodiments, the system 100 can performor extract work from the cabin discharge air. In this way, thepressurized air of the volume can be utilized by the system 100 toachieve certain operations required at different altitudes. Forinstance, the system 100 can provide a conditioned form of the thirdmedium F3 as a portion of the mixed medium provided to the volume 102and/or other system (e.g., the aircraft cabin, the combined flight deckand aircraft cabin, a cabin pressure control system). In a non-limitingembodiment, the pressurized air can be resupplied to the volume 102.This resupplied pressurized air can be referred to as recirculation air(e.g., air that is recirculated inside the volume 102).

Thus, based on modes of operation, the system 100 can mix the firstmedium F1, the second medium F2, and/or the third medium F3 at thedifferent mixing points within the system 100 to produce the mixedmedium, as indicated by thick-solid-lined arrows. The mixed medium canbe mixed air that meet fresh air requirements set by aviationorganizations. The system 100 illustrates mixing point M1 and M2, whichare not limiting.

The system 100 can comprise a ram circuit. The ram circuit comprises ashell 105 encasing one or more heat exchangers. The shell 105 canreceive and direct a medium (such as ram air described herein) throughthe system 100. The one or more heat exchangers are devices built forefficient heat transfer from one medium to another. Examples of heatexchangers include double pipe, shell and tube, plate, plate and shell,adiabatic wheel, plate fin, pillow plate, and fluid heat exchangers.

The one or more heat exchangers encased by the shell 105 can be referredto as ram heat exchangers. Ram heat exchangers receive ram air, whichcan be outside air being forced through the shell 105, as a heat sink tocool bleed air (e.g., the first medium F1) and/or fresh air (e.g., thesecond medium F2). As shown in FIG. 1, the shell 105 comprises a primaryheat exchanger 106 and a secondary heat exchanger 107. In a non-limitingembodiment, an exhaust of the cabin discharge air can be releasedthrough the shell 105 of the ram circuit and used in conjunction or inplace of the ram air.

Also, as shown in FIG. 1, the system can include an outflow heatexchanger 108. In a non-limiting embodiment, an exhaust of the cabindischarge air (e.g., the third medium F3) can be released through theoutflow valve (a.k.a. an outflow control valve and a thrust recoveryoutflow valve). For example, when the third medium F3 from the outflowheat exchanger 108 is coupled to the outflow valve, the outflow heatexchanger 108 increases the energy in the third medium F3, whichincreases the thrust recovered by the outflow valve. Note that thepressure drop at a high altitude between overboard and one of the inlet101, the volume 102, and the inlet 103 can cause a corresponding mediumto be pulled through the components of the system 100.

The system 100 can comprise a compressing device 109. The compressingdevice 109 can comprise a compressor 112, a turbine 113, a power turbine114, a fan 116, and a shaft 118.

The compressing device 109 is a mechanical device that includescomponents for performing thermodynamic work on the medium (e.g.,extracts or works on the first medium F1, the second medium F2, and/orthe third medium F3 by raising and/or lowering pressure and by raisingand/or lowering temperature). Examples of the compressing device 109include an air cycle machine, a three-wheel air cycle machine, afour-wheel air cycle machine, etc.

The compressor 112 is a mechanical device that raises a pressure of amedium and can be driven by another mechanical device (e.g., a motor ora medium via a turbine). Examples of compressor types includecentrifugal, diagonal or mixed-flow, axial-flow, reciprocating, ionicliquid piston, rotary screw, rotary vane, scroll, diaphragm, air bubble,etc. As shown in FIG. 1, the compressor 112 can receive and pressurizethe second medium F2 from the inlet 103.

The turbine 113 and the power turbine 114 are mechanical devices thatexpand and extract work from a medium (also referred to as extractingenergy). In the compressing device 109, the turbine drives thecompressor 112 and the fan 116 via the shaft 118. The turbine 113 can bea dual entry turbine that includes a plurality of inlet gas flow paths,such as an inner flow path and an outer flow path, to enable mixing ofalternative medium flows at the exit of the turbine. The inner flow pathcan be a first diameter, and the outer flow path can be a seconddiameter. The power turbine 114 can provide power assist to the turbine113 based on the mode of operation the system (as described herein). Ina non-limiting embodiment, the turbine 113 can comprise a first nozzleconfigured to accelerate the first medium for entry into a turbineimpeller and a second nozzle is configured to accelerate the secondmedium for entry into the turbine impeller. The turbine impeller can beconfigured with a first gas path configured to receive the first mediumfrom the first nozzle and with a second gas path configured to receivethe second medium from the second nozzle.

The fan 116 (e.g., a ram air fan as shown in FIG. 1) is a mechanicaldevice that can force via push or pull methods the medium (e.g., ramair) through the shell 105 across the heat exchangers 106 and 107 at avariable cooling to control temperatures.

The system 100 also comprises a water extractor 151, a condenser 162,and a water extractor 164. The water extractor 151 and the waterextractor 164 are mechanical devices that perform a process of takingwater from a medium. The condenser 160 is particular type of heatexchanger (another example includes a reheater). In a non-limitingembodiment, a condenser and/or a water extractor can combine to be ahigh pressure water separator that removes moisture at a highestpressure within an environmental control system (e.g., downstream of theprimary heat exchanger 106). A low-pressure water separator removesmoisture at a lowest pressure within an environmental control system,such as at a turbine discharge pressure (e.g., mixed air exiting theturbine 113).

The elements of the system 100 are connected via valves, tubes, pipes,and the like. Valves (e.g., flow regulation device or mass flow valve)are devices that regulate, direct, and/or control a flow of a medium byopening, closing, or partially obstructing various passageways withinthe tubes, pipes, etc. of the system 100. Valves can be operated byactuators, such that flow rates of the medium in any portion of thesystem 100 can be regulated to a desired value. For instance, a valve V1controls whether a flow of the second medium F2 from the secondary heatexchanger 107 bypasses the condenser 162 in accordance with a mode ofthe system 100. Further, a valve V2 controls whether a flow of the thirdmedium F3 from the volume 102 bypasses the power turbine 114 inaccordance with a mode of the system 100. Note that a combination ofcomponents and elements of the system 100 can be referred to as an airconditioning pack or a pack. The pack can exist between the inlet 101,the volume 102, the inlet 103, the outlet 104, and an exhaust of theshell 105.

Operational embodiments of the system 100 of FIG. 1 will now bedescribed with respect to an aircraft. The system 100 can be referred toas an advanced pneumatic system that mixes fresh air (e.g., the secondmedium F2) with bleed air (e.g., the first medium F1) to produce mixedair (e.g., the mixed medium) according to these operational embodiments.The (dual entry) turbine 113, the compressor 112, and the fan 116 canreceive energy from the bleed air, the cabin discharge air (e.g., thethird medium F3), and the fresh air. Operational embodiments can bedescribed as modes or operational modes. A first mode, which can be usedfor ground and/or low altitude flight conditions (such as ground idle,taxi, take-off, and hold conditions), is a low altitude operation of theaircraft. A second mode, which can be used for high altitude flightconditions (such as high altitude cruise, climb, and descent flightconditions), is a high altitude operation of the aircraft.

When the system 100 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from thebleed air via turbine 113 to compress the fresh air. The act ofcompressing the fresh air adds energy to the fresh air and that energyis also used to drive the compressor 112, in a bootstrapping effect, andthe fan 116. Note that, in the first mode, the valve V2 directs thecabin discharge air to bypass the power turbine 114 and flow to theoutlet 104, as the additional energy is not needed for compression.

For example, in the first mode, high-pressure high-temperature bleed airfrom either then the engine or the auxiliary power unit (e.g., the inlet101) enters the primary heat exchanger 106. The primary heat exchanger106 cools the high-pressure high-temperature bleed air to nearly ambienttemperature to produce cool high-pressure bleed air. The coolhigh-pressure bleed air enters the condenser 162, where it is cooled(and dehumidified) to produce cold high-pressure bleed air. Note thatthe heat sink used by the condenser 162 can be the mixed air exhaustingfrom the turbine 113 of the compressing device 109. The coldhigh-pressure bleed air flows through the water extractor 164, wheremoisture can be removed to produce cold dry high-pressure bleed air.Note that the combination of the condenser 162 and the water extractor164 can be considered a high-pressure water extractor because bleed airreceived by the condenser 162 is at the highest pressure in the system100. The cold dry high-pressure bleed air enters the turbine 113. Thecold dry high-pressure bleed air enters the turbine 113 through a firstnozzle, where it is expanded and work extracted.

The work extracted by the turbine 113 drives the compressor 112 used tocompress the fresh air and drives the fan 116 used to move ram airthrough the ram air heat exchangers (e.g., the primary heat exchanger106 and the secondary heat exchanger 107). The act of compressing thefresh air heats (and compresses) it to produce compressed fresh air,which is at a middle-pressure (i.e., medium-pressure fresh air). Themedium-pressure fresh air enters the outflow heat exchanger 108 and iscooled by the cabin discharge air to produce cooled medium-pressurefresh air. The cooled medium-pressure fresh air enters the secondaryheat exchanger 107, where it is further cooled to nearly ambienttemperature to produce cool pressurized fresh air. The cool pressurizedfresh air then enters the water extractor 151 where any free moisture inthe cool pressurized fresh air is removed to produce dry coolpressurized fresh air. This dry cool pressurized fresh air is thendirected by the valve V1 to the turbine 113. The dry cool pressurizedfresh air enters the turbine 113 through a second nozzle, where it isexpanded and work extracted.

The two air flows (i.e., the fresh air from the water extractor 151 andthe bleed air from the water extractor 164) are mixed at the turbine 113(e.g., at mixing point M1 as shown) to produce the mixed air. The mixedair leaves the turbine 113 and enters the condenser 162 (to cool thecool high-pressure bleed air leaving the primary heat exchanger 106 inthe condenser 162). The mixed air is then sent to condition the volume102.

When the system 100 is operating in the second mode (the high altitudeoperation of the aircraft), the system 100 can operate in a similar wayas in the low altitude operation. For instance, the compressor 112receives energy from the bleed air via turbine 113 to compress the freshair. The act of compressing the fresh air adds energy to the fresh air.However, this energy is not enough to further drive the compressor 112.The compressor 112 then also receives energy from the cabin dischargeair via the power turbine 114 (the valve V2 directs the third medium F3to the power turbine 114), which used to increase an amount of the freshair compressed in the compressor 112. Further, the dry cool pressurizedfresh air exiting the water extractor 151 is also directed by the valveV1 to a mixing point M2 so that the fresh air is mixed downstream of theturbine 113 (rather than at it). Furthermore, in the second mode, freshair requirements can be met by mixing the bleed air with fresh air,while an amount of bleed air can reduced by 40% to 75% depending on analtitude. In this way, the system 100 provides the bleed air reductionranging from 40% to 75% to provide higher efficiencies with respect toengine fuel burn than contemporary airplane air systems.

Turning now to FIGS. 2 and 3, variations of the above system are shownas systems 200 and 300 according to non-limiting embodiments. Componentsof the above system that are similar to the systems 200 and 300 havebeen reused for ease of explanation, by using the same identifiers, andare not re-introduced. Note that, in these systems 200 and 300, thecompressing device 109 is divided into multiple components, so that thefan 116 can be located on a second shaft and driven by a mechanism otherthan the compressor 112.

Turning now to FIG. 2, the system 200 is shown. Alternative and/oradditional components of the system 200 include a compressing device 209that comprises a component 210 and a component 216. The component 210comprises the compressor 112, the turbine 113, and the power turbine 114on the same shaft 118. The component 216 comprises a turbine 217, ashaft 218, and a fan 219. The turbine 217 of the component 216 isconfigured to receive a flow of a first medium F1.2 (e.g., bleed air)from the inlet 101, so that energy of the flow of the first medium F1.2can be extracted by the turbine 217 and drive the fan 219 via the shaft218.

When the system 200 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from afirst flow of the first medium F1 via turbine 113 to compress the secondmedium F2 (e.g., fresh air). The act of compressing the second medium F2adds energy to the second medium F2 and that energy is also used todrive the compressor 112 in a bootstrapping effect. The fan 219 receivesenergy from the second flow of the first medium F1.2 passing through theturbine 217. Note that the pressure drop during the first mode betweenthe inlet 101 and the exhaust of the turbine 215 can cause the secondflow of the first medium F1.2 to be pulled through the turbine of thesystem 200.

When the system 200 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 113 to compress the secondmedium F2. The act of compressing the second medium F2 adds energy tothe second medium F2; however, this energy is not enough to furtherdrive the compressor 112. The compressor 112 then also receives energyfrom the third medium F3 via the power turbine 114 (the valve V2 directsthe third medium F3 to the power turbine 114), which is used to increasean amount of the second medium F2 compressed in the compressor 112.

Turning now to FIG. 3, the system 300 is shown. Alternative and/oradditional components of the system 300 include a compressing device 309that comprises the component 210 and a component 316. The component 316comprises a motor 317, a shaft 318, and a fan 319. The motor 317 of thecomponent 316 can be configured to receive electric power, which enablesthe motor 316 to drive the fan 319 via the shaft 318.

When the system 300 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 113 to compress the secondmedium F2. The act of compressing the second medium F2 adds energy tothe second medium F2 and that energy is also used to drive thecompressor 112 in a bootstrapping effect. The fan 319 is driven by themotor 317.

When the system 300 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 113 to compress the secondmedium F2. The act of compressing the second medium F2 adds energy tothe second medium F2; however, this energy is not enough to furtherdrive the compressor 112. The compressor 112 then also receive energyfrom the third medium F3 via the power turbine 114 (the valve V2 directsthe third medium F3 to the power turbine 114), which is used to increasean amount of the second medium F2 compressed in the compressor 112.

Turning now to FIGS. 4, 5, and 6, variations of the above systems areshown as systems 400, 500, and 600 according to non-limitingembodiments. Components of the above systems that are similar to thesystems 400, 500, and 600 have been reused for ease of explanation, byusing the same identifiers, and are not re-introduced.

With respect to FIG. 4, the system 400 is shown. Alternative and/oradditional components of the system 400 include a compressing device 409that additionally comprises dual use turbines 413 and 415, along with amixing point M3. The dual use turbines 413 and 415, the compressor 112,and the fan 116 can receive energy from the first medium F1 (e.g., bleedair) and the second medium F2 (e.g., fresh air).

When the system 400 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 and the fan 116 receiveenergy from the bleed air via turbine 415 and energy from the fresh airvia the turbine 413. The energy received by the compressor 112 isutilized to compress the fresh air. The act of compressing the fresh airadds energy to the fresh air and that energy is also used to drive thecompressor 112, in a bootstrapping effect, and the fan 116.

For example, in the first mode, high-pressure high-temperature bleed airfrom either then the engine or the auxiliary power unit (e.g., the inlet101) enters the primary heat exchanger 106. The primary heat exchanger106 cools the high-pressure high-temperature bleed air to nearly ambienttemperature to produce cool high-pressure bleed air. The coolhigh-pressure bleed air enters the condenser 162, where it is cooled(and dehumidified) to produce cold high-pressure bleed air. Note thatthe heat sink used by the condenser 162 can be the mixed air exhaustingfrom the compressing device 409. The cold high-pressure bleed air flowsthrough the water extractor 164, where moisture can be removed toproduce cold dry high-pressure bleed air. Note that the combination ofthe condenser 162 and the water extractor 164 can be considered ahigh-pressure water extractor because bleed air received by thecondenser 162 is at the highest pressure in the system 100. The cold dryhigh-pressure bleed air enters the turbine 415. The cold dryhigh-pressure bleed air enters the turbine 415, where it is expanded andwork extracted.

The work extracted by the turbine 415 drives the compressor 112 used tocompress fresh air and drives the fan 116 used to move ram air throughthe ram air heat exchangers (e.g., the primary heat exchanger 106 andthe secondary heat exchanger 107). The act of compressing the fresh airheats (and compresses) it to produce compressed fresh air, which is at amiddle-pressure (i.e., medium-pressure fresh air). The medium-pressurefresh air enters the outflow heat exchanger 108 and is cooled by thecabin discharge air (e.g., the third medium F3) to produce cooledmedium-pressure fresh air. The cooled medium-pressure fresh air entersthe secondary heat exchanger 107, where it is further cooled to nearlyambient temperature to produce cooled pressurized fresh air. The cooledpressurized fresh air then enters the water extractor 151 where any freemoisture in the cooled pressurized fresh air is removed to produce drycooled pressurized fresh air. This dry cooled pressurized fresh air isthen directed by the valve V1 to the turbine 413. The dry cooledpressurized fresh air enters the turbine 413, where it is expanded andwork extracted.

The two air flows (i.e., the fresh air from the turbine 413 and thebleed air from the turbine 415) are mixed to produce the mixed air. Themixing can be at the turbine 415 (e.g., at mixing point M3 as shown).The mixed air enters the condenser 162 (to cool the cool high-pressurebleed air leaving the primary heat exchanger 106 in the condenser 162).The mixed air is then sent to condition the volume 102.

When the system 400 is operating in the second mode (the high altitudeoperation of the aircraft), the system 400 can operate in a similar wayas in the low altitude operation, but for the dry cooled pressurizedfresh air exiting the water extractor 151 being directed by the valve V1to a mixing point M2. That is, the fresh air is mixed downstream of thecondenser 162 and/or the turbine 415 rather than at it. Further, in thesecond mode, fresh air requirements can be met by mixing the bleed airwith fresh air, while an amount of bleed air can reduced by 40% to 60%depending on an altitude. In this way, the system 400 provides the bleedair reduction ranging from 40% to 60% to provide higher efficiencieswith respect to engine fuel burn than contemporary airplane air systems.Note that, in the second mode, the compressor 112 and fan 116 receiveenergy from the bleed air. The act of compressing the fresh air addsenergy to the fresh air.

Turning now to FIGS. 5 and 6, variations of the above systems are shownas systems 500 and 600 according to non-limiting embodiments. Componentsof the above systems that are similar to the systems 500 and 600 havebeen reused for ease of explanation, by using the same identifiers, andare not re-introduced. Note that, in these systems 500 and 600, thecompressing device 409 is divided into multiple components, so that thefan 116 can be located on a second shaft and driven by a mechanism otherthan the compressor 112.

With respect to FIG. 5, the system 500 is shown. Alternative and/oradditional components of the system 500 include a compressing device 509that comprises a component 510 and the component 216. The component 510comprises the compressor 112, the turbine 413, and the turbine 415 onthe same shaft 118. The component 216 comprises the turbine 217, theshaft 218, and the fan 219. The turbine 217 of the component 216 isconfigured to receive a flow of a first medium F1.2 (e.g., bleed air)from the inlet 101, so that energy of the flow of the first medium F1.2can be extracted by the turbine 217 and drive the fan 219 via the shaft218.

When the system 500 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from afirst flow of the first medium F1 via turbine 415 and energy from thesecond medium F2 (e.g., fresh air) via the turbine 413. The energyreceived by the compressor 112 is utilized to compress the second mediumF2. The act of compressing the second medium F2 adds energy to thesecond medium F2 and that energy is also used to drive the compressor112 in a bootstrapping effect. The fan 219 receives energy from thesecond flow of the first medium F1.2 passing through the turbine 217.Note that the pressure drop during the first mode between the inlet 101and the exhaust of the turbine 215 can cause the second flow of thefirst medium F1.2 to be pulled through the turbine of the system 500.

When the system 500 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 415 to compress the secondmedium F2. The act of compressing the second medium F2 adds energy tothe second medium F2.

Turning now to FIG. 6, the system 600 is shown. Components of the abovesystems that are similar to the system 600 have been reused for ease ofexplanation, by using the same identifiers, and are not re-introduced.Alternative and/or additional components of the system 600 include acompressing device 609 that comprises the component 510 and thecomponent 316. The component 510 comprises the compressor 112, theturbine 413, and the turbine 415 on the same shaft 118. The component316 comprises the motor 317, the shaft 318, and the fan 319. The motor317 of the component 316 can be configured to receive electric power,which enables the motor 316 to drive the fan 319 via the shaft 318.

When the system 600 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from afirst flow of the first medium F1 via turbine 415 and energy from thesecond medium F2 (e.g., fresh air) via the turbine 413. The energyreceived by the compressor 112 is utilized to compress the second mediumF2. The act of compressing the second medium F2 adds energy to thesecond medium F2 and that energy is also used to drive the compressor112 in a bootstrapping effect. The fan 319 is driven by the motor 317.

When the system 600 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 415 to compress the secondmedium F2. The act of compressing the second medium F2 adds energy tothe second medium F2.

Turning now to FIGS. 7, 8, and 9, variations of the above systems areshown as systems 700, 800, and 900 according to non-limitingembodiments. Components of the above systems that are similar to thesystems 700, 800, and 900 600 have been reused for ease of explanation,by using the same identifiers, and are not re-introduced.

With respect to the system 700 of FIG. 7, alternative and/or additionalcomponents of the system 700 include a compressing device 709 thatadditionally comprises a (dual use) turbine 713 and a turbine 715, alongwith mixing point M5. Note that turbine 713 is a duel entry turbine,that the mixing point M5 is downstream of the heat exchangers 106 and107, and that the third medium F3 can be supplied to an inlet of the ramcircuit based on the operation of a valve v7. The exhaust of the turbine713 can be controlled a valve V7, such that the flow of can be directedto an outlet 104 (into the ram circuit) or mixed at the turbine 715(mixing point M5).

When the system 700 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 and the fan 116 receiveenergy from the first medium F1 via turbine 715 and energy from thesecond medium F2 via the turbine 713. The energy received by thecompressor 112 is utilized to compress the second medium F2. The act ofcompressing the second medium F2 adds energy to the second medium F2 andthat energy is also used to drive the compressor 112, in a bootstrappingeffect, and the fan 116. Note that the second medium F2 and the firstmedium F1 can mix at the turbine 715 (mixing point M5).

When the system 700 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 and the fan 116 receiveenergy from the first medium F1 via turbine 715 and energy from thethird medium F3 via the turbine 713. The energy received by thecompressor 112 is utilized to compress the second medium F2. Note thatthe second medium F2 and the first medium F1 can mix downstream of theturbine 715 (e.g., at mixing point M2). Note that the third medium F3 isdirected by valve V7 to outlet 104.

Turning now to FIGS. 8 and 9, variations of the above systems are shownas systems 800 and 900 according to non-limiting embodiments. Componentsof the above systems that are similar to the systems 800 and 900 havebeen reused for ease of explanation, by using the same identifiers, andare not re-introduced. Note that, in these systems 800 and 900, thecompressing device 709 is divided into multiple components, so that thefan 116 can be located on a second shaft and driven by a mechanism otherthan the compressor 112.

With respect to FIG. 8, the system 800 is shown. Alternative and/oradditional components of the system 800 include a compressing device 809that comprises a component 810 and the component 216. The component 810comprises the compressor 112, the turbine 713, and the turbine 715 onthe same shaft 118. The component 216 comprises the turbine 217, theshaft 218, and the fan 219. The turbine 217 of the component 216 isconfigured to receive a flow of a first medium F1.2 (e.g., bleed air)from the inlet 101, so that energy of the flow of the first medium F1.2can be extracted by the turbine 217 and drive the fan 219 via the shaft218.

When the system 800 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst medium F1 via turbine 715 and energy from the second medium F2 viathe turbine 713. The energy received by the compressor 112 is utilizedto compress the second medium F2. The act of compressing the secondmedium F2 adds energy to the second medium F2 and that energy is alsoused to drive the compressor 112, in a bootstrapping effect. Note thatthe second medium F2 and the first medium F1 can mix at the turbine 715(mixing point M5). The fan 219 receives energy from the second flow ofthe first medium F1.2 passing through the turbine 217. Note that thepressure drop during the first mode between the inlet 101 and theexhaust of the turbine 215 can cause the second flow of the first mediumF1.2 to be pulled through the turbine of the system 700.

When the system 800 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst medium F1 via turbine 715 and energy from the third medium F3 viathe turbine 713. The energy received by the compressor 112 is utilizedto compress the second medium F2. Note that the second medium F2 and thefirst medium F1 can mix downstream of the turbine 715 (e.g., at mixingpoint M2). Note that the third medium F3 is directed by valve V7 tooutlet 104.

With respect to the system 900 of FIG. 9, alternative and/or additionalcomponents of the system 900 include a compressing device 909 thatcomprises the component 810 and the component 316. The component 810comprises the compressor 112, the turbine 713, and the turbine 715 onthe same shaft 118. The component 316 comprises the motor 317, the shaft318, and the fan 319. The motor 317 of the component 316 can beconfigured to receive electric power, which enables the motor 316 todrive the fan 319 via the shaft 318.

When the system 900 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst medium F1 via turbine 715 and energy from the second medium F2 viathe turbine 713. The energy received by the compressor 112 is utilizedto compress the second medium F2. The act of compressing the secondmedium F2 adds energy to the second medium F2 and that energy is alsoused to drive the compressor 112, in a bootstrapping effect. Note thatthe second medium F2 and the first medium F1 can mix at the turbine 715(mixing point M5). The fan 319 is driven by the motor 317.

When the system 900 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receive energy from thefirst medium F1 via turbine 715 and energy from the third medium F3 viathe turbine 713. The energy received by the compressor 112 is utilizedto compress the second medium F2. Note that the second medium F2 and thefirst medium F1 can mix downstream of the turbine 715 (e.g., at mixingpoint M2). Note that the third medium F3 is directed by valve V7 tooutlet 104.

Turning now to FIG. 10, a variation of the above systems is shown assystem 1000 according to non-limiting embodiments. Components of theabove systems that are similar to the systems 1000 have been reused forease of explanation, by using the same identifiers, and are notre-introduced. Alternative and/or additional components of the system1000 include a compressing device 1009 that the component 210(comprising the compressor 112, the turbine 113, and the power turbine114 on the same shaft 118) and a component 1016 (comprising a turbine1017, a shaft 1-18, and a fan 1019). In general, the compressor 112 canreceive energy from the first medium F1 via the turbine 113 and thethird medium F3 via the power turbine 114, and the fan 1019 can receiveenergy from the second medium F2. A valve V10 can be utilized to bypassthe turbine 1017 according to a mode.

In low altitude operation the compressor, in the system 1000, receivesenergy from the first medium F1. The act of compressing the secondmedium F2 adds energy to the second medium F2 and that energy is used todrive the fan. When the system 1000 is operating in the first mode (thelow altitude operation of the aircraft), the compressor 112 receivesenergy from the first medium F1. The operations by the turbine 1017extracts energy from the second medium F2 and that energy is also usedto drive the fan 1019.

When the system 1000 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst medium F1. The act of compressing the second medium F2 adds energyto the second medium F2 but not enough to further drive the fan 1019.The compressor 112 can also receive energy from the third medium F3 viathe power turbine 1015, which is used to increase an amount of thesecond medium F2 compressed in the compressor 112.

Turning now to FIGS. 11, 12, and 13, variations of the above systems areshown as systems 1100, 1200, and 1300 according to non-limitingembodiments. Components of the above systems that are similar to thesystems 1100, 1200, and 1300 have been reused for ease of explanation,by using the same identifiers, and are not re-introduced.

With respect to the system 1100 of FIG. 11, alternative and/oradditional components of the system 1100 include a compressing device1109 that comprises a turbine 1113, along with mixing point M11 and avalve V11. Note that the mixing point M11 is downstream of the heatexchangers 106 and 107 and upstream of the turbine 1113. The exhaust ofthe secondary heat exchanger 107 can be controlled a valve V11, suchthat the flow of can be directed to the volume 102 (mixing point M2) orthe turbine 1113 (via mixing point M11).

When the system 1100 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from themixed air via turbine 1113 to compress the fresh air. The act ofcompressing the fresh air adds energy to the fresh air and that energyis also used to drive the compressor 112, in a bootstrapping effect, andthe fan 116. Note that, in the first mode, the valve V2 directs thecabin discharge air to bypass the power turbine 114 and flow to theoutlet 104, as the additional energy is not needed for compression.

For example, in the first mode, high-pressure high-temperature bleed airfrom either then the engine or the auxiliary power unit (e.g., the inlet101) enters the primary heat exchanger 106. The primary heat exchanger106 cools the high-pressure high-temperature bleed air to nearly ambienttemperature to produce cool high-pressure bleed air. The coolhigh-pressure bleed air enters the condenser 162, where it is cooled(and dehumidified) to produce cold high-pressure bleed air. Note thatthe heat sink used by the condenser 162 can be the mixed air exhaustingfrom the turbine 1113 of the compressing device 109. The coldhigh-pressure bleed air flows through the water extractor 164, wheremoisture can be removed to produce cold dry high-pressure bleed air.Note that the combination of the condenser 162 and the water extractor164 can be considered a high-pressure water extractor because bleed airreceived by the condenser 162 is at the highest pressure in the system1100. The cold dry high-pressure bleed air is mixed with an exhaust ofthe water extractor 151 to produce mixed air. The mixed air enters theturbine 1113, where it is expanded and work extracted.

The work extracted by the turbine 1113 drives the compressor 112 used tocompress the fresh air and drives the fan 116 used to move ram airthrough the ram air heat exchangers (e.g., the primary heat exchanger106 and the secondary heat exchanger 107). The act of compressing thefresh air heats (and compresses) it to produce compressed fresh air,which is at nearly the same pressure as the bleed air. The pressurizedfresh air enters the outflow heat exchanger 108 and is cooled by thecabin discharge air to produce cooled pressurized fresh air. The cooledpressurized fresh air enters the secondary heat exchanger 107, where itis further cooled to nearly ambient temperature to produce coolpressurized fresh air. The cool pressurized fresh air is then directedby the valve V1 to the water extractor 151 where any free moisture inthe cool pressurized fresh air is removed to produce dry coolpressurized fresh air. This dry cool pressurized fresh air is mixed withan exhaust of the water extractor 164 to produce the mixed air. Themixed air enters the turbine 1113, where it is expanded and workextracted.

The two air flows (i.e., the fresh air from the water extractor 151 andthe bleed air from the water extractor 164) are mixed downstream of theturbine 1113 (e.g., at mixing point M11 as shown) to produce the mixedair. The mixed air leaves the turbine 1113 and enters the condenser 162(to cool the cool high-pressure bleed air leaving the primary heatexchanger 106 in the condenser 162). The mixed air is then sent tocondition the volume 102.

When the system 1100 is operating in the second mode (the high altitudeoperation of the aircraft), the system 1100 can operate in a similar wayas in the low altitude operation. For instance, the compressor 112receives energy from the bleed air via turbine 1113 to compress thefresh air. The act of compressing the fresh air adds energy to the freshair. However, this energy is not enough to further drive the compressor112. The compressor 112 then also receives energy from the cabindischarge air via the power turbine 114 (the valve V2 directs the thirdmedium F3 to the power turbine 114), which used to increase an amount ofthe fresh air compressed in the compressor 112. Further, the dry coolpressurized fresh air exiting the water extractor 151 is also directedby the valve V11 to a mixing point M2 so that the fresh air is mixeddownstream of the turbine 1113 (rather than at it). Furthermore, in thesecond mode, fresh air requirements can be met by mixing the bleed airwith fresh air, while an amount of bleed air can reduced by 40% to 60%depending on an altitude. In this way, the system 100 provides the bleedair reduction ranging from 40% to 60% to provide higher efficiencieswith respect to engine fuel burn than contemporary airplane air systems.

Turning now to FIGS. 12 and 13, variations of the above system are shownas systems 1200 and 1300 according to non-limiting embodiments.Components of the above system that are similar to the systems 1200 and1300 have been reused for ease of explanation, by using the sameidentifiers, and are not re-introduced. Note that, in these systems 1200and 1300, the compressing device 1109 is divided into multiplecomponents, so that the fan 116 can be located on a second shaft anddriven by a mechanism other than the compressor 112.

Turning now to FIG. 12, the system 1200 is shown. Alternative and/oradditional components of the system 200 include a compressing device1209 that comprises a component 1210 and a component 216. The component1210 comprises the compressor 112, the turbine 1113, and the powerturbine 114 on the same shaft 118. The component 216 comprises theturbine 217, the shaft 218, and the fan 219. The turbine 217 of thecomponent 216 is configured to receive a flow of a first medium F1.2(e.g., bleed air) from the inlet 101, so that energy of the flow of thefirst medium F1.2 can be extracted by the turbine 217 and drive the fan219 via the shaft 218.

When the system 1200 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from themixed air via turbine 1113 to compress the second medium F2 (e.g., freshair). The act of compressing the second medium F2 adds energy to thesecond medium F2 and that energy is also used to drive the compressor112 in a bootstrapping effect. The fan 219 receives energy from thesecond flow of the first medium F1.2 passing through the turbine 215.Note that the pressure drop during the first mode between the inlet 101and the exhaust of the turbine 215 can cause the second flow of thefirst medium F1.2 to be pulled through the turbine of the system 1200.

When the system 1200 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst medium F1 via turbine 1113 to compress the second medium F2. Theact of compressing the second medium F2 adds energy to the second mediumF2; however, this energy is not enough to further drive the compressor112. The compressor 112 then also receives energy from the third mediumF3 via the power turbine 114 (the valve V2 directs the third medium F3to the power turbine 114), which is used to increase an amount of thesecond medium F2 compressed in the compressor 112.

Turning now to FIG. 13, the system 1300 is shown. Alternative and/oradditional components of the system 1300 include a compressing device1309 that comprises the component 1210 and the component 316. Thecomponent 1210 comprises the compressor 112, the turbine 1113, and thepower turbine 114 on the same shaft 118. The component 316 comprises themotor 317, the shaft 318, and the fan 319. The motor 317 of thecomponent 316 can be configured to receive electric power, which enablesthe motor 316 to drive the fan 319 via the shaft 318.

When the system 1300 is operating in the first mode (the low altitudeoperation of the aircraft), the compressor 112 receives energy from themixed air via turbine 1113 to compress the second medium F2. The act ofcompressing the second medium F2 adds energy to the second medium F2 andthat energy is also used to drive the compressor 112 in a bootstrappingeffect. The fan 319 is driven by the motor 317.

When the system 1300 is operating in the second mode (the high altitudeoperation of the aircraft), the compressor 112 receives energy from thefirst flow of the first medium F1 via turbine 1113 to compress thesecond medium F2. The act of compressing the second medium F2 addsenergy to the second medium F2; however, this energy is not enough tofurther drive the compressor 112. The compressor 112 then also receiveenergy from the third medium F3 via the power turbine 114 (the valve V2directs the third medium F3 to the power turbine 114), which is used toincrease an amount of the second medium F2 compressed in the compressor112.

Aspects of the embodiments are described herein with reference toflowchart illustrations, schematics, and/or block diagrams of methods,apparatus, and/or systems according to embodiments. Further, thedescriptions of the various embodiments have been presented for purposesof illustration, but are not intended to be exhaustive or limited to theembodiments disclosed. Many modifications and variations will beapparent to those of ordinary skill in the art without departing fromthe scope and spirit of the described embodiments. The terminology usedherein was chosen to best explain the principles of the embodiments, thepractical application or technical improvement over technologies foundin the marketplace, or to enable others of ordinary skill in the art tounderstand the embodiments disclosed herein

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting. As used herein, thesingular forms “a”, “an” and “the” are intended to include the pluralforms as well, unless the context clearly indicates otherwise. It willbe further understood that the terms “comprises” and/or “comprising,”when used in this specification, specify the presence of statedfeatures, integers, steps, operations, elements, and/or components, butdo not preclude the presence or addition of one more other features,integers, steps, operations, element components, and/or groups thereof.

The flow diagrams depicted herein are just one example. There may bemany variations to this diagram or the steps (or operations) describedtherein without departing from the spirit of embodiments herein. Forinstance, the steps may be performed in a differing order or steps maybe added, deleted or modified. All of these variations are considered apart of the claims.

While the preferred embodiment has been described, it will be understoodthat those skilled in the art, both now and in the future, may makevarious improvements and enhancements which fall within the scope of theclaims which follow. These claims should be construed to maintain theproper protection.

What is claimed is:
 1. A compressing device, comprising: a turbinecomprising a first inlet and a second inlet and configured to provideenergy by expanding one or more mediums, wherein the first inlet isconfigured to receive a first medium of the one or more mediums, andwherein the second inlet is configured to receive a second medium of theone or more mediums; and a compressor configured to: receive a firstenergy derived from the first and second mediums being expanded acrossthe turbine during a first mode of the compressing device, receive asecond energy derived from the first medium being expanded across theturbine during a second mode of the compressing device, and compress thesecond medium in accordance with the first mode or the second mode. 2.The compressing device of claim 1, comprising: a fan configured toreceive the first energy during the first mode and the second energyduring the second mode.
 3. The compressing device of claim 1,comprising: a power turbine configured to provide a third energy byexpanding a third medium of the one or more mediums, wherein thecompressor is configured to receive the third energy from the thirdmedium expanded across the power turbine.
 4. The compressing device ofclaim 1, comprising: a first component comprising the turbine and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan, a second turbine, and a shaft.
 5. Thecompressing device of claim 4, wherein the fan is driven via the shaftby the first medium expanding across the second turbine.
 6. Thecompressing device of claim 1, comprising: a first component comprisingthe turbine and the compressor; and a second component, which isseparate from the first component, comprising a fan driven by a motor.7. The compressing device of claim 1, wherein the first medium and thesecond medium are mixed at the turbine during the first mode.
 8. Thecompressing device of claim 1, wherein the first medium and the secondmedium are mixed downstream of the turbine during the second mode. 9.The compressing device of claim 1, wherein the first medium is bleed airand the second medium is fresh air.
 10. An environmental control systemof an aircraft comprising the compressing device of claim
 1. 11. Acompressing device, comprising: a first turbine configured to provide afirst energy by expanding a first medium; a second turbine configured toprovide a second energy by expanding a second medium; and a compressorconfigured to: receive the first energy and the second energy during afirst mode of the compressing device, receive the first energy during asecond mode of the compressing device, and compress the second medium inaccordance with the first mode or the second mode.
 12. The compressingdevice of claim 11, comprising: a fan configured to receive: the firstenergy and the second energy during the first mode, and the first energyduring the second mode.
 13. The compressing device of claim 11,comprising: a first component comprising the first turbine, the secondturbine, and the compressor; and a second component, which is separatefrom the first component, comprising a fan, a third turbine, and ashaft.
 14. The compressing device of claim 13, wherein the fan is drivenvia the shaft by the first medium expanding across the second turbine.15. The compressing device of claim 11, comprising: a first componentcomprising the first turbine, the second turbine, and the compressor;and a second component, which is separate from the first component,comprising a fan driven by a motor.
 16. The compressing device of claim11, wherein the second turbine comprises a dual entry turbine configuredto operate as a power turbine during a second mode by expanding a thirdmedium to provide a third to the compressor.
 17. The compressing deviceof claim 16, comprising: a first component comprising the first turbine,the second turbine, and the compressor; and a second component, which isseparate from the first component, comprising a fan, a third turbine,and a shaft.
 18. The compressing device of claim 16, comprising: a firstcomponent comprising the first turbine, the second turbine, and thecompressor; and a second component, which is separate from the firstcomponent, comprising a fan driven by a motor.
 19. A compressing device,comprising: a first turbine configured to receive and expand a firstmedium; a second turbine configured to receive and expand a secondmedium; and a compressor configured to: receive a first energy from theexpansion of the first medium by the first turbine, and compress thesecond medium in the first energy; and a fan configured to receive asecond energy from the expansion of the second medium by the secondturbine.
 20. The compressing device of claim 1, comprising: a powerturbine configured to provide a third energy by expanding a thirdmedium, wherein the compressor is configured to receive the third energyfrom the third medium expanded across the power turbine.
 21. Acompressing device, comprising: a turbine comprising a first inletconfigured to receive a mixture of a first medium and a second mediumand a second inlet configured to receive the first medium, wherein theturbine is configured to provide a first energy by expanding the mixtureand to provide a second energy by expanding the first medium; acompressor configured to: receive the first energy from the turbineduring a first mode of the compressing device, receive the second energyfrom the first medium during a second mode of the compressing device,and compress the second medium in accordance with the first mode or thesecond mode.
 22. The compressing device of claim 21, comprising: a fanconfigured to receive the first energy during the first mode and thesecond energy during the second mode.
 23. The compressing device ofclaim 21, comprising: a power turbine configured to provide a thirdenergy by expanding a third medium, wherein the compressor is configuredto receive the third energy from the third medium expanded across thepower turbine.
 24. The compressing device of claim 21, comprising: afirst component comprising the turbine and the compressor; and a secondcomponent, which is separate from the first component, comprising a fan,a second turbine, and a shaft.
 25. The compressing device of claim 24,wherein the fan is driven via the shaft by the first medium expandingacross the second turbine.
 26. The compressing device of claim 21,comprising: a first component comprising the turbine and the compressor;and a second component, which is separate from the first component,comprising a fan driven by a motor.